Software » Aerodynamics
AAS (Aerodynamic Analysis System)
A user friendly computer based tool for generation of aerodynamic data for Space Transportation Systems. The Aerodynamic Analysis System (AAS) as a whole is a framework with defined interfaces to allow integration of customers own aerodynamic predictions software. Developed in conjunction with GMV (Spain) and HTG (Germany) for use by ESA. The AAS consists of a number of modules, the Geometry Generation Module (GGM), the Aerodynamic Data Module (ADM) and the Post processing Module (PM). The GGM includes a graphical interface for vehicle design, output is IGES compatible. Software currently included within the ADM are data sheet schemes for subsonic/ transonic/supersonic speed regimes and the FGE panel based FRENEW code for the hypersonic regime. The ADM includes software for 'simplification' of complex vehicles for use within the data sheet methods where the geometries are limited to basic geometric shapes. Predictions are obtained for vehicle 'elements'. i.e. body, wing, tail, etc, and tables of aerodynamic data for these elements are output. Further tables of interference factors, i.e. wing-body, body-wing are also output allowing the aerodynamics of a complete vehicle to be generated from a number of constituent elements and hence an interface to a trajectory model. The inclusion of customer supplied data in the generation of the tabulated output is allowed. Predictions using the ADM have been compared with database and/or experimental measurement data for the US Space Shuttle, Apollo and the AGARD HB2 shape. Predictions using the methods within the ADM have also been compared very favourably with Navier Stokes (FGE, SPIKE) predictions.
NEAR FREE MOLECULAR
NEMESYS
Direct Simulation Monte Carlo solution 3D flowfield code for low density flows. Uses 'Maximum Entropy' thermochemical routines, computes behaviour of 'individual' molecular collision and surface interaction phenomena, including chemical kinetics.
Developed by FGE for application to non-continuum flowfield problems i.e. very high altitude atmosphere flight vehicles, vacuum plant and also in higher density flows where the feature scale of interest is the same order as the molecular mean free path.
FREE MOLECULAR/NEWTONIAN
FRENEW
Free molecular/Newtonian aerodynamics engineering prediction method for the aerothermodynamic behaviour of 3D vehicles in the atmosphere. Uses bridging functions to link between inviscid and free molecular regimes. FGE developed, code tested against complex (i.e. US Space Shuttle) geometries. Robust code used for initial scoping of aerodynamics and heating of arbitrary shaped bodies.
Uses correlations to boundary layer heating solutions along inviscid surface streamlines.
BOUNDARY LAYER & HEATING SOFTWARE
RKHMP
Axisymmetric/2D kinetic heating prediction method. Basic code, using integral equations (laminar/turbulent).
Cranfield Institute of Technology development, modified and used extensively for real gases by FGE for heat shield heating calculations.